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公开(公告)号：US11994089B2
公开(公告)日：2024-05-28
申请号：US16837143
申请日：2020-04-01
Applicant: United Technologies Corporation
Inventor： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis
CPC classification number: F02K3/06 , F04D29/323 , F01D17/162 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/12 , F05D2240/35 , F05D2260/40311 , F05D2260/74 , F05D2260/79
Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.
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2.发明授权公开(公告)号：US11598223B2
公开(公告)日：2023-03-07
申请号：US16227271
申请日：2018-12-20
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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公开(公告)号：US11566567B2
公开(公告)日：2023-01-31
申请号：US16656206
申请日：2019-10-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis
Abstract: A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.
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公开(公告)号：US11448123B2
公开(公告)日：2022-09-20
申请号：US14734035
申请日：2015-06-09
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Daniel Bernard Kupratis
Abstract: A gas turbine engine includes a fan bypass ratio greater than 12. A speed reduction device includes a gear ratio of at least 2.6. A turbine section includes a transition duct that is located between a high pressure turbine and a low pressure turbine and includes fewer support struts than vanes in a first vane row of the low pressure turbine.
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公开(公告)号：US11098655B2
公开(公告)日：2021-08-24
申请号：US16380605
申请日：2019-04-10
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis
Abstract: A gas turbine engine includes an engine spool with a turbine section, a propeller, a motor, and a variable drive arrangement. The variable drive arrangement mechanically couples the engine spool to the propeller, and includes a first gear connection rotationally coupled to the propeller, a second gear connection rotationally coupled to the engine spool, and a sprag clutch rotationally coupled to the first gear connection. The sprag clutch is configured to passively decouple the motor from the first gear connection when a torque input from the engine spool exceeds a torque input from the motor, and is configured to passively couple the motor to the first gear connection when the torque input from motor exceeds a torque input from the engine spool.
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Patent Agency Ranking
公开(公告)号：US10954857B2
公开(公告)日：2021-03-23
申请号：US16012295
申请日：2018-06-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis
Abstract: A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.
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公开(公告)号：US10907540B2
公开(公告)日：2021-02-02
申请号：US16299430
申请日：2019-03-12
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Jacob Shubinski
Abstract: A turbine section for a gas turbine engine includes an independently controllable wheel downstream of the first static vane structure and a turbine rotor downstream of the independently controllable wheel. A method of generating thrust for a gas turbine engine, includes rotating a independently controllable wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.
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公开(公告)号：US20200291784A1
公开(公告)日：2020-09-17
申请号：US16299430
申请日：2019-03-12
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Jacob Shubinski
Abstract: A turbine section for a gas turbine engine includes a variable reaction free wheel downstream of the first static vane structure and a turbine rotor downstream of the variable reaction free wheel. A method of generating thrust for a gas turbine engine, includes rotating a variable reaction free wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.
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公开(公告)号：US10738694B1
公开(公告)日：2020-08-11
申请号：US16110473
申请日：2018-08-23
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Dmitriy B. Sidelkovskiy , Neil Terwilliger , William G. Sheridan
Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.
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公开(公告)号：US10724395B2
公开(公告)日：2020-07-28
申请号：US16148442
申请日：2018-10-01
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Sean Danby
Abstract: A gas turbine engine includes a turbine section that is configured to drive a fan through a fan shaft. The fan includes a plurality of fan blades rotatable about an axis of rotation of the gas turbine engine. A fan nacelle includes a first electrical machine component. The fan is located within the fan nacelle. A plurality of fan inlet guide vanes includes a second electrical machine component. The plurality of fan inlet guide vanes are rotatable about the axis.
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